Burner with dilution opening

Abstract

A gas turbine engine includes a compressor section and a combustion section arranged in series along the engine centerline. The combustion section has a burner liner, a dome wall coupled to the burner liner and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and at least partially defined by the burner liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.

Description

[0001] Cross-reference to related applications

[0002] This application claims priority to U.S. Provisional Application Serial No. 63 / 296,682, filed January 5, 2022, the contents of which are incorporated herein by reference. Technical Field

[0003] This topic generally relates to burners with dilution openings, and more specifically, to burners with a set of dilution openings located in the dome wall. Background Art

[0004] A gas turbine engine is driven by a flow of combustion gases through the engine to rotate multiple turbine blades. A combustor may be located within the gas turbine engine and fluidly connected to the turbine through which the combustion gases flow.

[0005] The use of hydrocarbon fuels in the combustors of gas turbine engines is known. Generally, air and fuel are fed into the combustion chamber, where they mix, and the fuel is then burned in the presence of air to produce hot gases. These hot gases are then fed to the turbine, where they are cooled and expanded to generate power. Byproducts of fuel combustion typically include toxins harmful to the environment, such as nitrogen oxides and nitrogen dioxide (collectively known as NO). x ), CO, UHC (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides, including oxides of sulfur (e.g., SO2 and SO3).

[0006] One solution to reduce environmentally harmful compounds is to use fuels other than hydrocarbons. Hydrogen, or hydrogen mixed with another element or compound, can be used for combustion, but hydrogen or hydrogen-blended fuels result in higher flame temperatures than conventional fuels. That is, hydrogen or hydrogen-blended fuels typically have a wider flammability range and a faster combustion rate compared to conventional fuels such as petroleum-based fuels or mixtures of petroleum and synthetic fuels.

[0007] Standards originating from global air pollution problems regulate nitrogen oxides (NOx) generated by the operation of gas turbine engines. x Emissions include unburned hydrocarbons (UHC) and carbon monoxide (CO). In particular, nitrogen oxides (NOx) are formed within the burner during operation due to the high flame temperature. x The desired effect is to reduce NO by adjusting the distribution and / or mode within the burner. x Emissions can be reduced while maintaining the desired efficiency. Attached Figure Description

[0008] In the attached diagram:

[0009] Figure 1This is a schematic diagram of a gas turbine engine.

[0010] Figure 2 Depicting the combustion zone along the gas turbine engine Figure 1 The cross-sectional view of line II-II.

[0011] Figure 3 It is a cross-sectional view of a burner in a combustion section formed by a burner liner having multiple sets of dilution openings, according to one aspect of the present invention.

[0012] Figure 4 It is based on one aspect disclosed in this article and has the characteristics of... Figure 3 A schematic diagram of a variant of section II, which is used for the first set of dilution openings of the burner.

[0013] Figure 5 This is based on one aspect disclosed in this article. Figure 3 The first set of dilution openings is a variant.

[0014] Figure 6 It is based on one aspect disclosed herein, having a dome-shaped wall from Figure 5 A variant of part III.

[0015] Figure 7 It is based on another aspect disclosed herein, having a dome-shaped wall. Figure 5 Another variant of Part III.

[0016] Figure 8 It is based on one aspect disclosed herein, having a first set of dilution openings from Figure 3 A schematic diagram of a partial IV variant.

[0017] Figure 9 It is based on another aspect disclosed herein, having a first set of dilution openings from Figure 3 A schematic diagram of a partial IV variant.

[0018] Figure 10 It is based on one aspect disclosed herein, having a first set of dilution openings from Figure 3 A schematic diagram of a partial IV variant.

[0019] Figure 11 It is based on another aspect disclosed in this article, also located in Figure 3 Region IV from Figure 10 A schematic diagram of the first set of dilution openings.

[0020] Figure 12 It is based on another aspect disclosed herein, having a first set of dilution openings from Figure 3 A schematic diagram of a partial IV variant.

[0021] Figure 13 It is based on one aspect disclosed herein, having a flare cone and a dome wall. Figure 3 A schematic diagram of a partial V variation.

[0022] Figure 14 It is based on another aspect disclosed herein, having a flared cone and a dome wall. Figure 3 A schematic diagram of a partial V variation.

[0023] Figure 15 This is based on another aspect disclosed in this article. Figure 2 A variation of a portion of the cross-sectional view.

[0024] Figure 16 The diagram shows the arrangement of the dome walls surrounding the engine's centerline. Figure 2 A schematic diagram of the variation of the combustion zone.

[0025] Figure 17-21 It is located in such Figure 16 The exemplary distribution of the first, second, third, fourth, and fifth dilution openings in the first group of dilution openings described herein within the dome wall arranged in the middle. Detailed Implementation

[0026] The aspects of the disclosure described herein relate to combustors, and more particularly to combustor liners with dilution openings. For illustrative purposes, this disclosure will be described in relation to gas turbine engines. However, it will be understood that the aspects of the disclosure described herein are not limited thereto, and the combustors described herein can be implemented in engines, including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines. The aspects of the disclosure discussed herein are generally applicable to non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0027] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0028] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0029] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0030] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "front" indicate what is in front of something, and "backward" or "rear" indicate what is behind something. For example, when used in relation to fluid flow, forward / front can indicate upstream, and backward / rear can indicate downstream.

[0031] The term "fluid" can refer to either a gas or a liquid. The term "fluid connectivity" means that fluids can establish connections between specified areas.

[0032] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a gas turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0033] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used for identification purposes only to aid the reader in understanding this disclosure and do not create limitation, particularly regarding the location, orientation, or use of aspects of the disclosure described herein. Connective references (e.g., attachment, connection, joint, and engagement) are to be interpreted broadly and may include structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connective reference does not necessarily mean that two elements are directly connected and fixed relative to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0034] The singular forms “a,” “an,” and “the” include plural references unless the context clearly indicates otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0035] As used herein and throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” “substantially,” and “basically” are not limited to the specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, and / or a range of defined values. Scope limitations are combined and interchanged herein and throughout the specification and claims; such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints can be combined independently of each other.

[0036] Figure 1 This is a schematic diagram of a gas turbine engine 10. As a non-limiting example, the gas turbine engine 10 can be used within an aircraft. The gas turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16 arranged in a series flow configuration. A drive shaft 18 rotatably connects the compressor and turbine sections 12, 16, such that rotation of one affects rotation of the other, and the drive shaft 18 defines the axis of rotation or engine centerline 21 of the gas turbine engine 10.

[0037] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 fluidly connected in series with each other. Turbine section 16 may include an LP turbine 26 and an HP turbine 28 fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, LP turbine 26, and HP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may connect the LP compressor 22 to the LP turbine 26, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 28. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 26, and LP drive shaft, such that rotation of the LP turbine 26 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, HP turbine 28, and HP drive shaft, such that rotation of the HP turbine 28 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0038] Compressor section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. The compressor blades for a stage of compressor section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of compressor section 12 may be mounted to a housing that may extend circumferentially around gas turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of stages may be possible. Furthermore, it is contemplated that any other number of components may be present within compressor section 12.

[0039] Similar to compressor section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. The turbine blades of one stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of the turbine section may be circumferentially mounted to the housing. It should be noted that any number of blades, blades, and turbine stages can be present, as the illustrated turbine section is merely schematic. Furthermore, it is contemplated that any other number of components may be present within turbine section 16.

[0040] Combustion section 14 may be arranged in series between compressor section 12 and turbine section 16. Combustion section 14 may be fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 28 at its downstream end.

[0041] During operation of the gas turbine engine 10, ambient air or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where it is compressed to define pressurized air. This pressurized air can then flow into the combustion section 14, where it mixes with fuel and is ignited to generate combustion gases. The HP turbine 28 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 26, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the gas turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 26 drives the LP spool to rotate the fan (not shown) and the LP compressor 22. The pressurized airflow and combustion gases together define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the gas turbine engine 10.

[0042] Figure 2 Depicting along Figure 1 A cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include an annular arrangement of fuel injectors 76 disposed around the engine centerline 21 of the gas turbine engine 10. Each fuel injector 76 may be connected to the combustor 80. It should be understood that the annular arrangement of fuel injectors may be one or more fuel injectors, and the one or more fuel injectors 76 may have different characteristics. Depending on the type of engine in which the combustor 80 is located, the combustor 80 may have a cylindrical, annular, or annular arrangement. In a non-limiting example, the annular arrangement is illustrated and disposed within the housing 78. The combustor 80 is defined by a combustor liner 82, which includes an outer annular combustor liner 82a and an inner annular combustor liner 82b that are concentric with each other and annularly surround the engine centerline 21. A dome assembly 84 including a dome wall 90, together with the combustor liner 82, may define an annular combustion chamber 86 surrounding the engine centerline 21. First and second sets of dilution openings 92, 93 may be located in the dome wall 90. The first and second sets of dilution openings 92, 93 may be arranged in a ring around the engine centerline 21. The first and second sets of dilution openings 92, 93 may be annular dilution openings defining a continuous ring around the engine centerline 21, as shown in the figure. The figure illustrates at least one fuel injector 76 of a plurality of fuel injectors arranged in a ring around the engine centerline 21, fluidly connected to the combustion chamber 86. The compressed air passage 88 may be at least partially defined by both the burner liner 82 and the housing 78.

[0043] Figure 3 Depicting along Figure 1The cross-sectional view obtained by line III-III shows combustion section 14. A third set of dilution openings 94 may be located in the burner liner 82, connecting the compressed air passage 88 and the burner 80.

[0044] Fuel injector 76 may be coupled to and disposed within dome assembly 84 upstream of flared cone 104 to define fuel / air mixture outlet 96. Fuel / air mixture outlet may define dome inlet 96 such that fuel / air mixture outlet and dome inlet are the same and fluidly connected to each other at flared cone 104. Fuel injector 76 may include fuel inlet 98 and linear fuel passage 100, fuel inlet 98 being adapted to receive fuel flow (F), linear fuel passage 100 extending between fuel inlet 98 and fuel / air mixture outlet / dome inlet 96. A first set of dilution openings 92 may define a swirler disposed at fuel / air mixture outlet / dome inlet 96 to cause incoming compressed air (C) to swirl near fuel (F) exiting fuel injector 76 and to provide a homogeneous mixture of air and fuel entering combustor 80.

[0045] Both the inner burner liner 82a and the outer burner liner 82b can have an outer surface 106 and an inner surface 108 that at least partially define the combustion chamber 86. The burner liner 82 can be comprised of a single continuous integral portion or multiple integral portions assembled together to define the inner burner liner 82a and the outer burner liner 82b. As a non-limiting example, the outer surface 106 can define a first piece of the burner liner 82, while the inner surface 108 can define a second piece of the burner liner 82, which, when assembled together, form the burner liner 82. As described herein, the burner liner 82 includes a third set of dilution openings 94. Further, it is contemplated that the burner liner 82 can be of any type, including but not limited to double-walled liners or ceramic liners. An igniter 110 can be disposed at the burner liner 82 and, as a non-limiting example, is fluidly connected to the combustion chamber 86 upstream of the third set of dilution openings 94.

[0046] During operation, compressed air (C) can flow from compressor section 72 to burner 80 through dome assembly 84. A first set of dilution openings 92 in dome wall 90 allows at least a portion of the compressed air (C) to flow from dome assembly 84 to combustion chamber 86, defining a first dilution flow (D1).

[0047] In addition, compressed air (C) can flow from compressor section 72 to burner 80 through compressed air passage 88. A third set of dilution openings 94 in burner liner 82 allows at least a portion of the compressed air (C), which defines a second dilution flow (D2), to flow from compressed air passage 88 to combustion chamber 86.

[0048] Some compressed air (C) can be mixed with fuel (F), and once it enters the combustor 80, the mixture is ignited in the combustion chamber 86 by one or more igniters 110 to generate combustion gas (G). The combustion gas (G) is mixed with dilution gas streams (D1, D2) supplied through multiple sets of dilution openings 92, 93, 94, and mixed in the combustion chamber 86. Afterward, the combustion gas (G) flows through the combustor outlet 112 and exits into the turbine section 74.

[0049] Figure 4 This is a schematic diagram of a portion of burner 180 (a variant of burner 80) according to another aspect disclosed herein. Burner 180 is substantially similar to part III of burner 80; therefore, similar portions will be identified by similarity numerals incremented by 100. It should be understood that the description of similar portions of burner 80 applies to burner 180 unless otherwise noted.

[0050] Combustor 180 has a combustion chamber 186 defined by a combustor liner 182 and a dome assembly 184 including a dome wall 190. A flared cone 204 may define a fuel / air mixture outlet / dome inlet 196 and a dome centerline (DC) extending from the geometric center of the flared cone 204. The dome centerline (DC) may be angled relative to the engine centerline 21 and substantially parallel to the engine centerline 21. Figure 2 The dome wall 190 may extend radially away from the dome centerline (DC). First and second sets of dilution openings 192a, 193a may be located within the dome wall 190, between the fuel / air mixture outlet / dome inlet 196 and the combustor liner 182. The first and second sets of dilution openings 192a, 193a may extend between the dilution inlet 122 and the dilution outlet 124, and include at least one impeller 120 disposed between the dilution inlet 122 and the dilution outlet 124. In one aspect, the first and second sets of dilution openings 192a, 193a may be annular around the engine centerline 21, forming concentric circles. Figure 1The first set of dilution openings 192a surrounds the second set of dilution openings 193a. Any number of blades 120 can be circumferentially oriented around the engine centerline 21. At least one blade 120 can be an axial flow or radial flow blade, or a combination of axial and radial flow blades. An axial flow blade moves the airflow in the axial direction along a principal longitudinal axis extending parallel to the dome centerline (DC). A radial flow blade moves the air in the radial direction along a principal vertical axis extending perpendicular to the dome centerline (DC). A pair of blades 120 can define a nozzle having a first dilution centerline (CL1) angled toward the dome centerline (DC) of the combustion chamber 186. The first dilution centerline (CL1) can form a dilution angle (α) of less than 90° with the dome centerline (DC). In some embodiments, the dilution angle (α) can be less than or equal to 60°.

[0051] The dome wall 190 extends from the flared cone 204 toward the outlet 124 of the first set of dilution openings 192 approximately perpendicular (within 5%) to the dome centerline (DC) to define a flat portion 116. At least one cooling hole 126 may be located where the dome wall 190 meets the combustion liner 182. The dome wall 190 between the outlet 124 and at least one cooling hole 126 may be angled toward the combustion liner 182 away from the fuel / air mixture outlet / dome inlet 196 to define a tapered portion 114 with an obtuse angle (β) between the dome wall 190 and the combustion liner 182. The obtuse angle (β) is greater than 90°. In some embodiments, the obtuse angle (β) may be greater than 130°. The tapered portion 114 may meet the flat portion 116 at a first junction 118. The flared cone 204 may meet the dome wall 190 at a second junction 128.

[0052] During operation, at least one impeller 120 can provide swirl (SF) to the combustion chamber 186. In addition, at least one cooling hole 126 can provide additional compressed air (C) for cooling the internal surface 208 of the combustion liner 182.

[0053] Figure 5 It is a variant used for burner 180. Figure 3 A schematic diagram of part II of burner 80. Figure 4A variation of the first and second sets of dilution openings 192a, 193a is shown as first and second sets of dilution openings 192b, 193b located in the dome wall 190, between the fuel / air mixture outlet / dome inlet 196 and the burner liner 182. In this variation, the second dilution centerline (CL2) is angled away from the dome centerline (DC) of the combustion chamber 186. The second dilution centerline (CL2) can still form a dilution angle (α) of less than 90° with the dome wall 190. In some embodiments, the dilution angle (α) can be less than or equal to 60°. However, in this particular variation, the outlet 124 points towards the burner liner 182. Therefore, it should be understood that the dilution angle (α) can vary between -60 and 60 degrees.

[0054] Figure 6 The example shown is a non-limiting one. Figure 5 A variation of the dome wall 190 in region III according to another aspect disclosed herein. The dome wall 190a may be angled to define a tapered portion 114a surrounding the outlet 124 of the first set of dilution openings 192b. The dome wall 190a may include a flat portion 116a extending radially from the second joint 128. The first joint 118 may define the starting point of the tapered portion 114a. The tapered portion 114a may extend radially from the first joint 118 toward the burner liner 182 to form an obtuse angle (β).

[0055] Figure 7 The example shown is a non-limiting one. Figure 5 Another variation of the dome wall 190 in region III, according to another aspect disclosed herein. The dome wall 190b may be angled to define a tapered portion 114b that extends radially from the second joint 128 toward the burner liner 182 to form an obtuse angle (β). The first joint 118 may still be located between the outlet 124 and the end 128 of the flared cone 204. The dome wall 190b may include a flat portion 116b extending radially from the first joint 118 around the outlet 124 of the first set of dilution openings 192b.

[0056] Although illustrated with identical cross-sections, it should be understood that any other portion of the dome walls 190, 190a, 190b, the conical portions 114, 114a, 114b, the flared cone 204, and the dome assembly 184 may be formed from substantially separate portions. By “meeting,” the portions described herein simply overlap at the first and second joints 118, 128 described herein. While a joint can mean physically joined together, it can also mean that point of overlap in space.

[0057] Figure 8 It is located in burner 80, which is a non-limiting example. Figure 3A schematic diagram of the first set of dilution openings 292 in region IV. The first set of dilution openings 292 is substantially similar to the first set of dilution openings 92; therefore, similar portions will be identified with similarity numbers incremented by 200. It should be understood that the description of similar portions of the first set of dilution openings 92 applies to the first set of dilution openings 292, unless otherwise noted.

[0058] The dome wall 290 may define a deflector 230, which has two parts: an inner section 230a and an outer section 230b. The outer section 230b may have a surface 232 located axially forward of the inner section 230a. A first set of dilution openings 292 may be disposed between the inner section 230a and the outer section 230b. The first set of dilution openings may include multiple rows 234 of impeller blades 220 arranged radially relative to each other.

[0059] Figure 9 It is located in burner 80, which is a non-limiting example. Figure 3 A schematic diagram of the first set of dilution openings 392 in region IV. The first set of dilution openings 392 is substantially similar to the first set of dilution openings 92; therefore, similar portions will be identified with similarity numbers incremented by 300. It should be understood that the description of similar portions of the first set of dilution openings 92 applies to the first set of dilution openings 392, unless otherwise noted.

[0060] A dome wall 390 may define a deflector 330 having an inner section 330a and an outer section 330b. The outer section 330b may have a surface 332 located axially forward of the inner section 330a. A first set of dilution openings 392 may be disposed between the inner section 330a and the outer section 330b. An axially extending channel 340 defining a third dilution centerline (CL3) may terminate in an outlet 324 on the deflector 330. The axially extending channel 340 may separate the inner section 330a from the outer section 330b. The axially extending channel 340 may define at least one opening in the first set of dilution openings 392. The axially extending channel 340 may include at least one blade 320 disposed within the channel 340 near the outlet 324.

[0061] Figure 10 It is located in burner 80, which is a non-limiting example. Figure 3 A schematic diagram of the first set of dilution openings 492a in region IV. The first set of dilution openings 492a is substantially similar to the first set of dilution openings 92; therefore, similar portions will be identified with similarity numbers incremented by 400. It should be understood that the description of similar portions of the first set of dilution openings 92 applies to the first set of dilution openings 492a, unless otherwise noted.

[0062] The dome wall 490 may define a deflector 430. The deflector 430 may include a plurality of axial deflectors 442, illustrated as two axial deflectors. The axial deflectors 442 may extend axially away from the dome wall 490. As a non-limiting example, a first set of dilution openings 492a may include three dilution openings radially arranged and separated by the axial deflectors 442. In other words, the first set of dilution openings 492a may be arranged within the dome wall 490 in an interleaved relationship with the axial deflectors 442. Each dilution opening in the first set of dilution openings 492a may be flush with the dome wall 490. The first set of dilution openings 492a may include at least one blade 420 or any number of blades 420 circumferentially oriented around the flared cone 504. Although illustrated as an axial flow blade 420a, at least one blade 420 may be axial or radial, or a combination of axial and radial flow blades.

[0063] The first axial deflector 442a can extend axially downstream from the dome wall 490 by a first distance (d1). The second axial deflector 442b can be positioned radially outward from the first axial deflector 442a. The second axial deflector 442b can extend axially downstream from the dome wall 490 by a second distance (d2), wherein the second distance (d2) is greater than the first distance (d1). The straight line 444 connecting the distal ends of the first and second axial deflectors 442a and 442b can be drawn to intersect the burner liner 482 at an obtuse angle (β).

[0064] The third set of dilution openings 446 may be located around the flared cone portion 504. The third set of dilution openings 446 may include a purge channel 448 extending between a purge inlet 450 and a purge outlet 452. An inlet chamber 454 may be fluidly connected at the purge inlet 450 to the first set of dilution openings 492a and the purge channel 448.

[0065] During operation, compressed air (C) can flow through the first set of dilution openings 492a to form a dilution flow (DF). In some embodiments, the flow through the first set of dilution openings 492a can form a swirling flow (SF). Any particles remaining in the inlet chamber 454 can be removed via the third set of dilution openings 446 as a purge flow (P). The fuel / air (F / C) mixture can flow along the path shown by arrow 456. The purge flow (P) is further used to cool the flared cone 504 and ensure that the fuel / air (F / C) mixture does not adhere to the hot side of the dome wall 490. The path shown by arrow 456 can be controlled by a combination of the dilution flow (DF), the swirling flow (SF), and the purge flow (P).

[0066] Figure 11 The diagram shows Figure 10A variant of the first set of dilution openings 492a is numeralized as the first set of dilution openings 492b located in the dome wall 490, between the fuel / air mixture outlet / dome inlet 496 and the burner liner 482. For clarity, some part numbers have been removed.

[0067] The first set of dilution openings 492b may be at least partially defined by at least one blade 420 or any number of blades 420 circumferentially oriented around the flared cone 504. The first set of dilution openings 492b may include an inner opening 493a, an outer opening 493c, and an intermediate opening 493b disposed between the inner opening 493a and the outer opening 493c. The outer opening 493c may be located near the burner liner 482 and includes an axial flow blade 420a.

[0068] A pair of radial flow impellers, first and second radial flow impellers 420r and 421r, may be axially disposed upstream of the dome wall 490 and in fluid communication with the inlet gas chamber 454. A first axially extending channel 440a may extend from a first dilution inlet 422a at the first radial flow impeller 420r to a first dilution outlet 424a at the dome wall 490. The first radial flow impeller 420r may extend radially inward from the first dilution inlet 422a in a direction away from the burner liner 482. Although illustrated as extending radially inward, it should be understood that the first radial flow impeller 420r may extend radially outward, or both the first and second radial flow impellers 420r and 421r may extend radially outward.

[0069] The second axial extension channel 440b can extend from the second dilution inlet 422b at the second radial flow vane 421r to the second outlet 424b at the distal ends of the first and second axial deflectors 442a, 442b. The second radial flow vane 421r can extend radially outward from the second dilution inlet 422b in the direction toward the burner liner 482. Although illustrated as extending radially outward, it should be understood that the second radial flow vane 421r can extend radially inward, or both the first and second radial flow vanes 420r, 421r can extend radially inward.

[0070] In addition to or together with the flow previously described herein, during operation, compressed air (C) may travel through the first axial flow impeller 420a and be discharged near the combustor liner 482. Compressed air (C) near the fuel / air mixture outlet / dome inlet 496 may be radially drawn into the first axial extension channel 440a by the first radial flow impeller 420r. The second radial flow impeller 421r may mirror the first radial flow impeller 420r by drawing compressed air (C) from near the combustor liner 482 into the second axial extension channel 440b, and vice versa, depending on the impeller orientation. The radial flow impellers 420r and 421r may be recessed from the dome wall 490 to provide sufficient axial length for the flow to develop before exiting the dome wall 490.

[0071] Figure 12 It is located in burner 80, which is a non-limiting example. Figure 3 A schematic diagram of the first set of dilution openings 592 in region IV. The first set of dilution openings 592 is substantially similar to the first set of dilution openings 92; therefore, similar portions will be identified with similarity numbers incremented by 500. It should be understood that the description of similar portions of the first set of dilution openings 92 applies to the first set of dilution openings 592, unless otherwise noted.

[0072] The dome wall 590 may include a deflector 530 and an impact wall 558 spaced apart to define an intermediate gas chamber 560. As a non-limiting example, the first set of dilution openings 592 may include two dilution openings radially disposed within the dome wall 590. The first set of dilution openings 592 may be at least partially defined by an axial flow vane 520a extending between a dilution inlet 522 at the impact wall 558 and a dilution outlet 524 at the deflector 530.

[0073] The third set of dilution openings 546 may be located around the flared cone portion 604. The third set of dilution openings 546 may include a purge channel 548 extending between the purge inlet 550 and the purge outlet 552. The inlet chamber 554 may be fluidly connected to the purge channel 548 at the first set of dilution openings 592 and the purge inlet 550.

[0074] A set of impact holes 562 may be located in the impact wall 558 surrounding the dilution inlet 522 of the first set of dilution openings 592. The impact holes 562 may discharge into the impact chamber 560 for impacting the inner surface 564 of the deflector 530.

[0075] A set of membrane cooling holes 566 may be located in the deflector 530. The set of membrane cooling holes 566 can fluidly connect the impact chamber 560 to the outer surface 568 of the deflector 530. Further contemplated, the set of membrane cooling holes can fluidly connect one or a combination of the inlet chamber 554, the impact chamber 560, or the first set of dilution openings 592 to the outer surface 568.

[0076] It should be understood that although the cross-sectional view shown represents all the holes / openings in the same plane, each hole / opening can be distributed circumferentially around the fuel / air mixture outlet / dome inlet 596 in any suitable manner.

[0077] In addition to or together with the flows described herein, during operation, compressed air (C) may pass through a set of impact holes 562 and impact the inner surface 564 of the deflector 530 to define an impact flow (I). Compressed air (C) may pass through a set of film cooling holes 566 and be discharged onto the outer surface 568 to define a film cooling flow (FC).

[0078] Steering Figure 13 The illustration shows a location based on another aspect disclosed in this article. Figure 3 A schematic enlarged view of a variant arrangement of the flared cone 104 and dome wall 90 of burner 80 in part V. The flared cone 704 and dome wall 690 are substantially similar to those of the flared cone 104 and dome wall 90 of burner 80; therefore, similar portions will be identified by similar numerals increased by 600. It should be understood that the description of similar portions of the flared cone 104 and dome wall 90 applies to the flared cone 704 and dome wall 690, unless otherwise noted.

[0079] The flared cone 704 may define a fuel / air mixture outlet / dome inlet 696. Similar to the third set of dilution openings previously described herein, a third set of dilution openings 646 may be located around the flared cone 704. The third set of dilution openings 646 may include a purge channel 648 extending parallel to and close to the flared cone 704 between the purge inlet 650 and the purge outlet 652. The purge channel 648 may define a fourth centerline (CL4) angled away from the fuel / air mixture outlet / dome inlet 696.

[0080] The third set of dilution openings 646 may further include a peripheral dilution channel 649, which extends radially outward from the purge channel 648 between the dilution inlet 651 and the dilution outlet 653. The peripheral channel 649 may define a fifth dilution centerline (CL5) angled away from the fuel / air mixture outlet / dome inlet 696. The fourth and fifth dilution centerlines (CL4, CL5) may be parallel to each other, or within 20% of each other. The inlet chamber 654 may be fluidly connected to the third set of dilution openings 646 at inlets 650, 651.

[0081] Steering Figure 14 The illustration shows a location based on another aspect disclosed in this article. Figure 3 A schematic enlarged view of a variant arrangement of the flared cone 104 and dome wall 90 in part V of the burner 80. The flared cone 804 and dome wall 790 are... Figure 3 The flared cone 104 and dome wall 90 of the burner 80 are substantially similar; therefore, similar parts will be identified by similar numbers incremented by 700. It should be understood that the description of similar parts of the flared cone 104 and dome wall 90 applies to the flared cone 804 and dome wall 790, unless otherwise noted.

[0082] The flared cone 804 may define a fuel / air mixture outlet / dome inlet 796. Similar to the third set of dilution openings previously described herein, a third set of dilution openings 746 may be located around the flared cone 804. The third set of dilution openings 746 may include a purge channel 748 extending parallel to and close to the flared cone 804 between a purge inlet 750 and a purge outlet 752. The purge channel 748 may define a sixth dilution centerline (CL6) angled in a first direction toward the flared cone 804 as indicated by arrow 701, and then angled in a second direction away from the flared cone 804 as indicated by arrow 702. An inlet chamber 754 may be fluidly coupled to the third set of dilution openings 746 at the purge inlet 750. During operation, compressed air (C) may flow through the third set of dilution openings 746 to initially form an impingement flow (I). The impingement flow (I) can bypass the fuel / air mixture outlet / dome inlet 796 and be discharged as a purge flow (P) through outlet 752.

[0083] Steering Figure 15 The diagram shows a variation of a portion of a cross-sectional view of the combustion section 70 within the gas turbine engine 10. In this variation, the first set of dilution openings 92 can be segmented dilution openings, wherein the first set of dilution openings 92 are arranged circumferentially around the engine centerline 21 in a segmented annular arrangement within the dome wall 90, as shown in the diagram. Therefore, the impeller blades, as described herein, can also be arranged in a segmented configuration around the engine centerline 21.

[0084] Figure 16 It is combustion section 370 ( Figure 15 A cross-sectional view of a variant of the combustion section 70 shows the arrangement of dome walls 390 around the engine centerline 321. Each dome wall described below may include discrete dilution openings arranged around the engine centerline 321. This is Figure 2 The variation shown is an annular dilution opening.

[0085] Figure 17 It is similar to that described in this article and located within the dome wall 490. Figure 16 An exemplary distribution of a set of dilution openings 492 arranged in the middle. Although the first set of dilution openings 492 is represented by numbers, it should be understood that any set of dilution openings described herein is expected to be arranged in a circumferential array around the fuel / air mixture outlet / dome inlet 496.

[0086] Figure 18 It is as described in this article and located within the dome wall 390, such as Figure 16 A second exemplary distribution of a set of dilution openings 392 arranged in the middle. Although the first set of dilution openings 392 is represented by numbers, it should be understood that any set of dilution openings described herein is contemplated for arrangement around the fuel / air mixture outlet / dome inlet 396. In this particular arrangement, the dilution openings are located in the corners 393 of the dome wall 390.

[0087] Figure 19 It is as described in this article and located within the dome wall 390, such as Figure 16 An exemplary distribution of a set of dilution openings 392 arranged in the middle. Although the first set of dilution openings 392 is represented by numbers, it should be understood that any set of dilution openings described herein is arranged annularly around the fuel / air mixture outlet / dome inlet 396 for flame shaping and to prevent the burner liner 82 ( Figure 3 The high temperature on the surface.

[0088] Figure 20 It is as described in this article and located within the dome wall 390, such as Figure 16 A third exemplary distribution of a set of dilution openings 392 arranged in the middle. Although the first set of dilution openings 392 is represented by numbers, it should be understood that any set of dilution openings described herein is contemplated for arrangement around the fuel / air mixture outlet / dome inlet 396. In this particular arrangement, the dilution openings are slotted openings. Slotted openings can have any shape, such as, as a non-limiting example, runway-shaped, circular, or elliptical. Furthermore, slotted openings can be oriented in any suitable manner, such as, as a non-limiting example, at an angle relative to the radial direction, as shown in the figure.

[0089] Figure 21 It is as described in this article and located within the dome wall 390, such as Figure 16 A fourth exemplary distribution of a set of dilution openings 392 arranged in the middle. Although the first set of dilution openings 392 is represented by numbers, it should be understood that any set of dilution openings described herein is contemplated to be arranged around the fuel / air mixture outlet / dome inlet 396. A set of dilution openings 392 may be annular around the dome centerline (DC). In this particular arrangement, the set of dilution openings 392 is an annular slot-shaped opening arranged annularly around the fuel / air mixture outlet / dome inlet 396.

[0090] Any combination of variations of the exemplary dome wall and the dilution opening location described herein is contemplated. Figure 4-21 For illustrative purposes only and not intended to be limiting. The dilution orifice / groove opening can be any form described herein. The deflector as described herein can be supplied directly from the under-shroud area or implemented with a dual-pressure-drop design. The compressed air as described herein can be a dilution flow with swirling currents generated by axial / radial flow impellers as described herein. It should be understood that the dilution flow as described herein can be arranged around the swirler axis or the engine axis. Each exemplary arrangement produces a dilution flow that is directed to keep the hot gas away from the deflector and burner liner, thus preventing mixing away from the wall. The deflector as described herein can be cooled by back-side or membrane cooling, or both.

[0091] It should be understood that the dilution openings described herein are exemplary, as shown in the figures. Dilution openings can be organized in numerous different ways and, by way of non-limiting example, can include ribs, pin assemblies, loops, sub-loops, membrane openings, gas chambers, meshes, and turbulence generators of any shape or size. Dilution openings can include other flow enhancement devices, such as, by way of non-limiting example, small openings located behind the dilution openings. It is further contemplated that dilution openings can be part of an assembly of dilution openings. It is also contemplated that dilution openings can be complementary to and separate from an assembly of cooling openings positioned along the burner liner.

[0092] A method for controlling nitrogen oxides or NO in combustion gases (G) present in burner 80 x The method includes injecting a dilution stream (D) into a combustion chamber as described herein at an angle as described herein through a dilution opening located in a dome wall as described herein. The method may further include injecting a purge stream (P) into a burner as described herein.

[0093] The benefit associated with the burner liner and method described herein is a more uniform temperature distribution downstream of the dilution opening, which is equivalent to better NO reduction. xand burner outlet temperature distribution / pattern. Lower temperatures on the deflector and liner equate to better liner and deflector life. Furthermore, the dilution opening arrangement described herein enables control of the flame structure within the combustion chamber.

[0094] Although described in the context of a gas turbine engine, it should be understood that the combustor described herein can be used for engines with NO emissions. x Any engine with a combustor. It should be understood that the application of the disclosed aspects discussed herein can also be applied to engines with propeller sections or fan and supercharger sections, as well as turbojet engines and turbine engines.

[0095] Within the scope not described herein, different features and structures of the various embodiments may be combined or substituted for each other as needed. The fact that a feature is not illustrated in all embodiments does not mean that it cannot be illustrated in this way, but rather that it is done for the sake of brevity. Therefore, various features of different embodiments may be mixed and matched as needed to form new embodiments, regardless of whether the new embodiments are explicitly described. All combinations or substitutions of the features described herein are covered by this disclosure.

[0096] This written description uses examples to illustrate the aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice the disclosed aspects, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of the aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0097] Further aspects are provided by the subject matter of the following clauses:

[0098] A gas turbine engine includes: a compressor section and a combustion section arranged in series along an engine centerline, the combustion section including: a combustor liner; a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall; a fuel injector fluidly coupled to the dome inlet; a combustion chamber fluidly coupled to the fuel injector and at least partially defined by the combustor liner and the dome wall; and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber, the at least one set of dilution openings being arranged circumferentially around the engine centerline.

[0099] In a gas turbine engine according to any one of the foregoing clauses, the at least one set of dilution openings is a first set of dilution openings and a second set of dilution openings that are concentric with each other.

[0100] In the gas turbine engine according to any one of the foregoing clauses, at least one of the first set of dilution openings and the second set of dilution openings is an annular dilution opening.

[0101] In the gas turbine engine according to any one of the foregoing clauses, at least one of the first set of dilution openings and the second set of dilution openings is a segmented dilution opening.

[0102] The gas turbine engine according to any one of the foregoing clauses is characterized in that the at least one set of dilution openings extends between the dilution inlet and the dilution outlet at the dome wall.

[0103] The gas turbine engine according to any one of the foregoing clauses further includes at least one blade disposed within the at least one set of dilution openings between the dilution inlet and the dilution outlet.

[0104] In a gas turbine engine according to any one of the foregoing clauses, the at least one impeller is one of a radial flow impeller or an axial flow impeller.

[0105] The gas turbine engine according to any one of the foregoing clauses, wherein the dome inlet defines a dome centerline, and the at least one set of dilution openings defines a dilution centerline.

[0106] In a gas turbine engine according to any one of the foregoing clauses, the dilution centerline is a first centerline that is angled toward the longitudinal axis and intersects the dome centerline to define a dilution angle.

[0107] In a gas turbine engine according to any one of the foregoing clauses, the dome wall defines a tapered portion forming an obtuse angle with the burner liner, and the dome wall extends radially between the fuel injector and the burner liner to define a flat portion, wherein the flat portion and the tapered portion meet at a first joint.

[0108] The gas turbine engine according to any one of the foregoing clauses, wherein the at least one set of dilution openings is located in the conical portion.

[0109] The gas turbine engine according to any one of the foregoing clauses, wherein the tapered portion extends between the first joint and the burner liner.

[0110] The gas turbine engine according to any one of the foregoing clauses, wherein the at least one set of dilution openings is located in the flat portion.

[0111] In a gas turbine engine according to any one of the foregoing clauses, the flat portion extends between the first joint and the burner liner.

[0112] The gas turbine engine according to any one of the foregoing clauses further includes a flared cone portion disposed around the fuel injector, wherein the flared cone portion meets the flat portion at a second joint, and wherein the flat portion extends between the first joint and the second joint.

[0113] The gas turbine engine according to any one of the foregoing clauses further includes a flared cone portion disposed around the fuel injector, wherein the flared cone portion meets the tapered portion at a second engagement portion, and wherein the tapered portion extends between the first engagement portion and the second engagement portion.

[0114] The gas turbine engine according to any one of the foregoing clauses further includes a flared cone portion disposed around the fuel injector and a purge passage disposed around the flared cone portion.

[0115] The gas turbine engine according to any one of the foregoing clauses further includes at least one axial deflector.

[0116] The gas turbine engine according to any one of the foregoing clauses, wherein the dome wall includes a deflector and an impact wall spaced apart to define an intermediate gas chamber.

[0117] The gas turbine engine according to any one of the foregoing clauses, wherein the at least one set of dilution openings is arranged circumferentially around the dome inlet.

Claims

1. A gas turbine engine, characterized in that, The gas turbine engine includes: A compressor section and a combustion section are arranged in a series flow along the engine centerline, the combustion section comprising: Burner lining; A dome wall connected to the burner liner, and a dome inlet located in the dome wall; wherein the dome wall defines a tapered portion forming an obtuse angle with the burner liner; A fuel injector fluidly connected to the dome inlet; the dome wall extends radially between the fuel injector and the burner liner to define a flat portion, wherein the flat portion and the tapered portion meet at a first joint. A flared cone portion is provided around the fuel injector, wherein the flared cone portion meets the conical portion at a second joint, and wherein the conical portion extends between the first joint and the second joint; A combustion chamber fluidly connected to the fuel injector and at least partially defined by the burner liner and the dome wall; and At least one set of dilution openings located in the dome wall and fluidly connected to the combustion chamber, the at least one set of dilution openings being arranged circumferentially around the engine centerline.

2. The gas turbine engine according to claim 1, characterized in that, The at least one set of dilution openings refers to a first set of dilution openings and a second set of dilution openings that are concentric with each other.

3. The gas turbine engine according to claim 2, characterized in that, At least one of the first group of dilution openings and the second group of dilution openings is an annular dilution opening.

4. The gas turbine engine according to claim 2, characterized in that, At least one of the first group of dilution openings and the second group of dilution openings is a segmented dilution opening.

5. The gas turbine engine according to any one of claims 1 and 2, characterized in that, The at least one set of dilution openings extends between the dilution inlet and the dilution outlet at the dome wall.

6. The gas turbine engine according to claim 5, characterized in that, It further includes at least one impeller disposed within the at least one set of dilution openings between the dilution inlet and the dilution outlet.

7. The gas turbine engine according to claim 6, characterized in that, The at least one of the impeller blades is either a radial flow impeller blade or an axial flow impeller blade.

8. The gas turbine engine according to any one of claims 1 and 2, characterized in that, The dome inlet defines the dome centerline, and the at least one set of dilution openings defines the dilution centerline.

9. The gas turbine engine according to claim 8, characterized in that, The dilution centerline is a first centerline that is angled toward the longitudinal axis and intersects the dome centerline to define the dilution angle.

10. The gas turbine engine according to claim 1, characterized in that, The at least one set of dilution openings is located in the conical portion.

11. The gas turbine engine according to claim 10, characterized in that, The tapered portion extends between the first joint and the burner liner.

12. The gas turbine engine according to claim 1, characterized in that, The at least one set of dilution openings is located in the flat portion.

13. The gas turbine engine according to claim 12, characterized in that, The flat portion extends between the first joint and the burner liner.

14. The gas turbine engine according to claim 1, characterized in that, It further includes a flared cone portion disposed around the fuel injector, wherein the flared cone portion meets the flat portion at a second engagement.

15. The gas turbine engine according to claim 14, characterized in that, The flat portion extends between the first joint and the second joint.

16. The gas turbine engine according to any one of claims 1 and 2, characterized in that, It further includes a flared cone portion disposed around the fuel injector and a purge channel disposed around the flared cone portion.

17. The gas turbine engine according to any one of claims 1 and 2, characterized in that, It further includes at least one axial deflector.

18. The gas turbine engine according to any one of claims 1 and 2, characterized in that, The dome wall includes a deflector and an impact wall spaced apart to define an intermediate air chamber.

19. The gas turbine engine according to any one of claims 1 and 2, characterized in that, The at least one set of dilution openings is arranged circumferentially around the dome inlet.

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